Mars orbiter EMC test method and system

Abstract

The present invention provides a Mars orbiter EMC test method and system, including: state preparation for the electromagnetic compatibility test of the Mars orbiter; environmental noise test in a microwave darkroom; electromagnetic compatibility test between the Mars orbiter and the carrier rocket; electromagnetic compatibility test of the simulated flight process of the Mars orbiter in the Earth-Mars transfer stage; electromagnetic compatibility test of the simulated flight process of the Mars orbiter in the Mars orbiting stage; collating test data of the electromagnetic compatibility test of the Mars orbiter, and analyzing the test data. Compared with the prior art, the present invention can test the electromagnetic compatibility in the initial prototype development stage of the Mars orbiter, provide a basis for the electromagnetic compatibility design and improvement of the Mars orbiter in the prototype stage, and help ensure that the electromagnetic compatibility requirements of the lander and the carrier rocket are met after the Mars orbiter docks with the lander and the carrier rocket.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft testing technology, and in particular to an EMC testing method and system for a Mars orbiter. Background Art

[0002] As an important part of the Mars rover system, the Mars orbiter has many electronic devices inside, multiple radio frequency channels such as device-to-ground communication and inter-device communication, and the transmitter has high output power and the receiver has high sensitivity, so the electromagnetic environment of the whole device is complex. After the Mars orbiter is developed, it needs to be docked with the lander and rover for joint work, and it also involves the joint working state with the launch vehicle at the launch site. In order to ensure the electromagnetic self-compatibility of the Mars orbiter and avoid electromagnetic interference between the subsystem products, and to ensure the electromagnetic compatibility (EMC) between the Mars orbiter and the lander and rover, and the launch vehicle, and avoid electromagnetic interference when working together, in addition to the electromagnetic compatibility design and testing of each subsystem product, the Mars orbiter also needs to be tested for electromagnetic compatibility at the whole device level.

[0003] However, the design of the Mars orbiter for deep space exploration is significantly different from that of other previous spacecraft. The system-level electromagnetic compatibility test methods and processes of previous spacecraft cannot fully meet the electromagnetic compatibility test requirements of the Mars orbiter.

[0004] Patent document CN103048561A discloses an EMC test method for a deep space vehicle complex, including: powering off all detectors constituting the vehicle complex, calibrating the EMC test equipment, and detecting the background noise of the microwave darkroom; performing electromagnetic radiation and sensitivity tests on each detector; analyzing the test data of each detector to determine the suppression of mutual interference between the detectors of the vehicle complex; and performing electromagnetic self-compatibility tests on the vehicle complex. However, this method is an EMC test method for a deep space vehicle complex, and cannot fully meet the EMC test requirements of a single Mars orbiter. Summary of the invention

[0005] In view of the defects in the prior art, the object of the present invention is to provide a Mars orbiter EMC testing method and system.

[0006] A Mars orbiter EMC test method provided by the present invention includes:

[0007] Preparation steps: Prepare the state for electromagnetic compatibility testing of the Mars orbiter;

[0008] The first test step: perform environmental noise test in a microwave darkroom;

[0009] Second test step: Conduct electromagnetic compatibility test between the Mars orbiter and the launch vehicle;

[0010] The third test step: Conduct electromagnetic compatibility testing of the Mars orbiter during the simulated flight process of the Earth-Mars transfer phase;

[0011] Fourth test step: Conduct electromagnetic compatibility test of the simulated flight process of the Mars orbiter during the Mars orbit phase;

[0012] Data processing steps: Organize the test data of the electromagnetic compatibility test of the Mars orbiter and analyze the test data.

[0013] Preferably, the preparation step comprises:

[0014] Step S101: placing the Mars orbiter in a sealed state in a microwave darkroom;

[0015] Step S102: placing the Mars orbiter test system, the lander simulation equipment and the electromagnetic compatibility test system outside the microwave darkroom;

[0016] Step S103: The Mars orbiter in the microwave darkroom is interconnected with the Mars orbiter test system, the lander rover simulation equipment, and the test equipment in the electromagnetic compatibility test system outside the microwave darkroom through a through-wall test cable.

[0017] Preferably, the first testing step includes:

[0018] Step S201: The Mars orbiter is powered off;

[0019] Step S202: Powering on the Mars orbiter test system, the lander simulation equipment, and the auxiliary equipment in the microwave darkroom;

[0020] Step S203: Measure and record the ambient noise spectrum of the ambient noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system. If there is a strong interference signal in the measured ambient noise, check and locate the interference source of the strong interference signal, and isolate the wall-penetrating test cable or auxiliary equipment that leaks the strong interference signal or strengthen the coating with double-sided aluminum film.

[0021] Preferably, the second testing step comprises:

[0022] Step S301: Power on the Mars orbiter, set the working state according to the active segment, turn on the power supply to the lander and rover power supply and distribution equivalent device, and set the power load value of the lander and rover power supply and distribution simulator according to the active segment state of the lander and rover;

[0023] Step S302: placing a radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, with the central axis of the radiation emission test antenna pointing to the lower plate of the Mars orbiter, and measuring and recording the radiation emission data of the Mars orbiter by electromagnetic radiation emission test equipment;

[0024] Step S303: Place the radiation sensitivity test antenna near the Mars orbiter, adjust the distance between the radiation sensitivity test antenna and the side panel of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and use the electromagnetic radiation sensitivity test equipment to output the test signal according to the transmission signal frequency band and power of the launch vehicle's transmitter to monitor whether the locking state and telemetry state of the Mars orbiter's transponder have abnormal jumps.

[0025] Preferably, the third testing step comprises:

[0026] Step S401: setting the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase;

[0027] Step S402: measuring and recording the field strength of each pyrotechnic device to be installed position of the Mars orbiter by using the pyrotechnic device field strength test equipment to verify whether the field strength of each pyrotechnic device to be installed position meets the limit requirement;

[0028] Step S403: performing an electrostatic discharge test on the Mars orbiter by using an electrostatic discharge test device;

[0029] Step S404: testing the demodulation threshold of the transponder of the Mars orbiter through the radio frequency test subsystem;

[0030] Step S405: the Mars orbiter performs simulated flight according to typical stages of the flight process of the Earth-Mars transfer phase, and monitors the stability of telemetry signals of various subsystems of the Mars orbiter and the correctness of detection data of the payload subsystem during the simulated flight;

[0031] The fourth test step includes:

[0032] Step 501: each subsystem of the Mars orbiter is set to a working state according to the maximum working mode of the Mars orbiting flight phase;

[0033] Step 502: the lander rover inter-device communication simulator outputs an inter-device return signal, adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, and simultaneously observes the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the lander rover inter-device communication simulator sends a set of landing rover simulated telemetry data, which are received by the Mars orbiter inter-device communication machine and then forwarded by the integrated electronic subsystem and the measurement and control subsystem to the Mars orbiter test system, to check the consistency between the received landing rover simulated telemetry data and the data sent by the lander rover inter-device communication simulator.

[0034] A Mars orbiter EMC test system provided by the present invention comprises:

[0035] Preparation module: to prepare the state of electromagnetic compatibility test of Mars orbiter;

[0036] The first test module: environmental noise test in a microwave darkroom;

[0037] The second test module: Conduct electromagnetic compatibility test between the Mars orbiter and the launch vehicle;

[0038] The third test module: Conduct electromagnetic compatibility testing of the simulated flight process of the Mars orbiter during the Earth-Mars transfer phase;

[0039] The fourth test module: Conduct electromagnetic compatibility testing of the simulated flight process of the Mars orbiter during the Mars orbit phase;

[0040] Data processing module: organize the test data of the electromagnetic compatibility test of the Mars orbiter and analyze the test data.

[0041] Preferably, the preparation module comprises:

[0042] The first preparation submodule: placing the Mars orbiter in a sealed state in a microwave darkroom;

[0043] The second preparation submodule: placing the Mars orbiter test system, the lander rover simulation equipment and the electromagnetic compatibility test system outside the microwave darkroom;

[0044] The third preparation submodule: The Mars orbiter in the microwave darkroom is interconnected with the Mars orbiter test system, the lander rover simulation equipment and the test equipment in the electromagnetic compatibility test system outside the microwave darkroom through wall test cables.

[0045] Preferably, the first test module includes:

[0046] The first test submodule: put the Mars orbiter in a power-off state; power on the Mars orbiter test system, the lander simulation equipment and the auxiliary equipment in the microwave darkroom; measure and record the environmental noise spectrum of the environmental noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system. If there is a strong interference signal in the measured environmental noise, check and locate the interference source of the strong interference signal, and isolate the wall-penetrating test cable or auxiliary equipment that leaks the strong interference signal or strengthen the coating with double-sided aluminum film.

[0047] Preferably, the second test module includes:

[0048] The second test submodule: power on the Mars orbiter, set the working state according to the active segment, turn on the power supply to the lander and rover power supply equivalent device, and the lander and rover power supply and distribution simulator sets the power load value according to the active segment state of the lander and rover; place the radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, with the central axis of the radiation emission test antenna pointing to the lower plate of the Mars orbiter, and measure and record the radiation emission data of the Mars orbiter through electromagnetic radiation emission test equipment; place the radiation sensitivity test antenna near the Mars orbiter, adjust the distance between the radiation sensitivity test antenna and the side plate of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and output the test signal according to the transmission signal frequency band and power of the carrier rocket's transmitter through the electromagnetic radiation sensitivity test equipment to monitor whether the locking state and telemetry state of the Mars orbiter's transponder have abnormal jumps.

[0049] Preferably, the third test module includes:

[0050] The third test submodule: setting the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase; measuring and recording the field strength of each pyrotechnic installation position of the Mars orbiter through the pyrotechnic field strength test equipment, and verifying whether the field strength of each pyrotechnic installation position meets the limit requirement; performing an electrostatic discharge test on the Mars orbiter through the electrostatic discharge test equipment; testing the demodulation threshold of the Mars orbiter's transponder through the radio frequency test subsystem; the Mars orbiter simulates the flight according to the typical stages of the flight process in the Earth-Mars transfer phase, and monitoring the stability of the telemetry signals of each subsystem of the Mars orbiter and the correctness of the detection data of the payload subsystem during the simulated flight;

[0051] The fourth test module includes:

[0052] The fourth test submodule: the subsystems of the Mars orbiter are set to work in accordance with the maximum working mode of the Mars orbiting flight phase; the lander and rover inter-device communication simulator outputs the inter-device return signal, and adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, while observing the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the lander and rover inter-device communication simulator sends a set of landing rover simulated telemetry data, which are received by the Mars orbiter inter-device communication machine and then forwarded by the integrated electronic subsystem and the measurement and control subsystem to the Mars orbiter test system to check the consistency between the received landing rover simulated telemetry data and the data sent by the landing rover inter-device communication simulator.

[0053] Compared with the prior art, the present invention has the following beneficial effects:

[0054] 1. The present invention can test the electromagnetic compatibility of the Mars orbiter during the initial prototype development stage and verify the electromagnetic compatibility between the Mars orbiter and the carrier rocket.

[0055] 2. The present invention can verify the self-compatibility of each subsystem inside the Mars orbiter and the electromagnetic compatibility with the communication interface of the lander and rover, providing a basis for the electromagnetic compatibility design and improvement of the Mars orbiter in the prototype stage.

[0056] 3. The present invention helps to ensure that the electromagnetic compatibility requirements of the Mars orbiter, the lander and the launch vehicle are met after docking. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0058] Figure 1 It is a schematic diagram of the process of the present invention;

[0059] Figure 2 It is a structural schematic diagram of the present invention. DETAILED DESCRIPTION

[0060] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0061] Figure 1 It is a schematic diagram of the process of the present invention, such as Figure 1As shown, the present invention provides a Mars orbiter EMC test method, comprising:

[0062] Preparation steps: Prepare the state for electromagnetic compatibility testing of the Mars orbiter.

[0063] Figure 2 It is a structural schematic diagram of the present invention, such as Figure 2 As shown, it includes lander simulation equipment, a Mars orbiter in a microwave darkroom, a Mars orbiter test system and an electromagnetic compatibility test system.

[0064] Specifically, the landing rover simulation equipment is used to simulate the interface function and status of the landing rover and the Mars orbiter, including a landing rover power supply and distribution simulator, a landing rover wired measurement and control simulator, a landing rover inter-device communication simulator and an inter-device link adjustment device. The landing rover power supply and distribution simulator and the landing rover wired measurement and control simulator are connected to the Mars orbiter via a low-frequency cable, and the landing rover inter-device communication simulator and the inter-device link adjustment device are connected to the inter-device communication antenna in the microwave darkroom via a radio frequency cable; wherein, the landing rover power supply and distribution simulator is used to simulate the function of the landing rover receiving the power supply current and charging current of the Mars orbiter before the two devices are separated, the landing rover wired measurement and control simulator is used to simulate the wired measurement and control communication function between the landing rover and the Mars orbiter before the two devices are separated, the landing rover inter-device communication simulator is used to simulate the inter-device communication machine of the landing rover, and simulate the radio frequency wireless communication with the Mars orbiter after the two devices are separated, and the inter-device link adjustment device is used to attenuate and adjust the radio frequency signal between the Mars orbiter and the inter-device communication simulator. Multi-channel two-way communication between the inter-device link adjustment equipment and the landing rover inter-device communication simulator.

[0065] Among them, the separation of the two devices refers to the separation of the lander and the Mars exploration orbiter.

[0066] Specifically, the Mars orbiter test system includes a power supply subsystem, a low-frequency measurement and control subsystem, an attitude and orbit control test subsystem, a radio frequency test subsystem and a test software subsystem. The test subsystems are interconnected through a local area network. The power supply subsystem, the low-frequency measurement and control subsystem and the attitude and orbit control test subsystem are connected to the Mars orbiter through a drop-out plug and its low-frequency cable, and the radio frequency test subsystem is connected to the measurement and control antenna in the microwave darkroom through an radio frequency cable. Among them, the power supply subsystem provides charging and power supply current for the Mars orbiter, and the low-frequency measurement and control subsystem monitors and sets the state of the Mars orbiter through a low-frequency wired channel, such as monitoring the bus current, bus voltage, battery discharge switch state, etc. of the Mars orbiter, as well as setting the simulated separation state of the rocket, the discharge switch connection setting, and the discharge switch disconnection setting. The attitude and orbit control test subsystem performs dynamic simulation of the Mars orbiter's on-orbit flight, outputs simulation signals to the Mars orbiter's attitude and orbit control sensors, and collects the status of actuators such as flywheels; the RF test subsystem communicates telemetry signals and remote control signals with the Mars orbiter through the measurement and control antenna and RF wireless channel, including measurement and control baseband equipment, remote control signal up-converter, telemetry signal down-converter, and RF link adjustment equipment; the test software system is used to generate remote control commands, send them to the RF test subsystem, receive telemetry data demodulated from the telemetry signal by the RF test subsystem, and parse and display the telemetry data.

[0067] Among them, the power supply subsystem consists of 20 voltage-stabilizing source modules and distributors, which provide charging and power supply current for the Mars orbiter in constant current mode.

[0068] Among them, the attitude and orbit control test subsystem performs dynamic simulation of the Mars orbiter's in-orbit flight, and outputs simulation signals to the Mars orbiter's attitude and orbit control sensors. The attitude and orbit control test subsystem performs dynamic simulation of the Mars orbiter's in-orbit flight, and outputs simulation signals to the Mars orbiter's star sensor, gyroscope combination and other attitude and orbit control subsystem products.

[0069] It can be known that the electromagnetic test system includes radiation sensitivity test equipment, radiation emission test equipment, pyrotechnic field strength test equipment and electrostatic discharge test equipment. The radiation sensitivity test equipment includes a signal source, a power amplifier and a radiation sensitivity test antenna, which are used to perform the radiation sensitivity test project of the electromagnetic compatibility of the Mars orbiter; the radiation emission test equipment includes a radiation emission test antenna, a high-sensitivity broadband receiver and a data acquisition device, which are used to perform the radiation emission test project of the EMC of the Mars orbiter; the pyrotechnic field strength test equipment includes a field strength probe and a field strength monitor, which are used to measure the field strength near the pyrotechnics of the Mars orbiter; the electrostatic discharge test equipment is an electrostatic arc discharge simulation source, which is used to test the resistance of the Mars orbiter to electrostatic discharge.

[0070] Preferably, the preparation step comprises: step S101: placing the Mars orbiter in a sealed state in a microwave darkroom; step S102: placing the Mars orbiter test system, the lander rover simulation equipment and the electromagnetic compatibility test system outside the microwave darkroom; step S103: interconnecting the Mars orbiter in the microwave darkroom with the Mars orbiter test system, the lander rover simulation equipment and the test equipment in the electromagnetic compatibility test system outside the microwave darkroom via a through-wall test cable.

[0071] Specifically, the test cables and auxiliary equipment located in the microwave darkroom are covered with double-sided aluminum film to avoid electromagnetic interference to the EMC test of the Mars orbiter.

[0072] The first test step: perform environmental noise test in a microwave darkroom.

[0073] Preferably, the first test step includes: step S201: putting the Mars orbiter in a power-off state; step S202: powering on the Mars orbiter test system, the lander simulation equipment and the auxiliary equipment in the microwave darkroom; step S203: measuring and recording the environmental noise spectrum of the environmental noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system. If there is a strong interference signal in the measured environmental noise, check and locate the interference source of the strong interference signal, and isolate the wall-penetrating test cable or auxiliary equipment that leaks the strong interference signal or strengthen the coating with double-sided aluminum film.

[0074] Among them, the interference signal can be shielded by isolating the wall-penetrating test cable or auxiliary equipment that leaks strong interference signals or strengthening the coating with double-sided aluminum film.

[0075] The second test step: Conduct electromagnetic compatibility test between the Mars orbiter and the launch vehicle.

[0076] Preferably, the second test step includes: Step S301: power on the Mars orbiter, set the working state according to the active segment, turn on the power supply to the lander power supply and distribution equivalent device, and the lander power supply and distribution simulator sets the power load value according to the active segment state of the lander.

[0077] Specifically, after the Mars orbiter is powered on, each internal subsystem of the Mars orbiter is set to a working state according to the active segment.

[0078] It should be noted that the interior of the Mars orbiter contains multiple subsystems, illustratively including a circuit subsystem, and the internal subsystems refer to all subsystems.

[0079] Among them, the overall circuit subsystem of the Mars orbiter is connected to the power supply to the lander and rover power distribution equivalent device, and the lander and rover power supply and distribution simulator sets the power load value according to the active segment state of the lander and rover. The overall circuit subsystem is a combination of subsystems used for power supply functions in the Mars orbiter.

[0080] Step S302: Place the radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, with the central axis of the radiation emission test antenna pointing to the lower plate of the Mars orbiter, and measure and record the radiation emission data of the Mars orbiter through electromagnetic radiation emission test equipment.

[0081] The present invention does not limit the setting of the preset position, and illustratively, it can be 3 meters.

[0082] Specifically, the measurement frequency band of the electromagnetic radiation emission test equipment covers the occupied signal frequency band of the launch vehicle receiver, verifying whether the radiation emission signal power of the active segment state of the Mars orbiter meets the limit requirements at the occupied signal frequency band of the launch vehicle receiver.

[0083] Step S303: Place the radiation sensitivity test antenna near the Mars orbiter, adjust the distance between the radiation sensitivity test antenna and the side panel of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and use the electromagnetic radiation sensitivity test equipment to output the test signal according to the transmission signal frequency band and power of the launch vehicle's transmitter to monitor whether the locking state and telemetry state of the Mars orbiter's transponder have abnormal jumps.

[0084] Specifically, depending on whether an abnormal situation occurs, it can be verified whether the Mars orbiter can withstand the interference of the launch signal of the carrier rocket.

[0085] The third test step: Conduct electromagnetic compatibility testing of the Mars orbiter during the simulated flight process during the Earth-Mars transfer phase.

[0086] Preferably, the third test step includes: step S401: setting the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase; step S402: measuring and recording the field strength of each pyrotechnic installation position of the Mars orbiter by means of pyrotechnic field strength testing equipment, and verifying whether the field strength of each pyrotechnic installation position meets the limit requirement; step S403: performing an electrostatic discharge test on the Mars orbiter by means of an electrostatic discharge testing device.

[0087] Specifically, the test method of step S403 is to illuminate the sun angle meter on the solar sail panel with a strong flashlight. After the sun angle meter signal telemetry is stable, a discharge test is performed with an electrostatic arc discharge simulation source to monitor whether the sun angle meter signal telemetry and other subsystem telemetry have jumps and continuous abnormal conditions. Each sun angle meter is subjected to a discharge test in turn to verify the Mars orbiter's resistance to electrostatic discharge.

[0088] Step S404: Testing the demodulation threshold of the transponder of the Mars orbiter through the radio frequency test subsystem.

[0089] Specifically, the test method is to adjust the uplink remote control link attenuation of the RF test subsystem, and simultaneously observe the transponder's receiving signal level telemetry and remote control lock state telemetry, so that the transponder's receiving signal level telemetry is equal to the demodulation threshold level, and send a set of remote control self-test instructions to the Mars orbiter from the ground measurement and control antenna through the test software subsystem and the RF test subsystem to monitor the correct reception of the remote control instructions by the Mars orbiter, verify the correctness of the demodulation threshold in the wireless state of the transponder, and verify the electromagnetic compatibility of the transponder remote control signal reception and the operation of other subsystems when the Mars orbiter is in the maximum operating mode.

[0090] Among them, electromagnetic self-compatibility refers to the electromagnetic compatibility between various subsystems inside the Mars orbiter.

[0091] Step S405: The Mars orbiter performs simulated flight according to typical stages of the flight process during the Earth-Mars transfer phase, and monitors the stability of telemetry signals of various subsystems of the Mars orbiter and the correctness of detection data of the payload subsystem during the simulated flight.

[0092] Among them, the typical stages include the initial stage of the Earth-Mars transfer orbit, the mid-course correction stage, the deep space maneuvering stage, the braking and capture stage, etc.

[0093] Specifically, during the flight, the power supply interface and wired data communication interface setting programs with the lander are simulated through the lander simulation equipment, which monitors the stability of the telemetry signals of each subsystem of the Mars orbiter and the correctness of the detection data of the payload subsystem during the simulated flight, and verifies the self-compatibility of each subsystem of the Mars orbiter.

[0094] Fourth test step: Conduct electromagnetic compatibility test of the Mars orbiter during the simulated flight process in the Mars circum-Mars phase.

[0095] Preferably, the fourth test step includes: step 501: each subsystem of the Mars orbiter sets the working state according to the maximum working mode of the Mars orbiting flight stage; step 502: the landing rover inter-device communication simulator outputs the inter-device return signal, adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, and observes the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine at the same time, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the landing rover inter-device communication simulator sends a set of landing rover simulation telemetry data, and after the Mars orbiter inter-device communication machine receives it, it is forwarded by the integrated electronic subsystem and the measurement and control subsystem and then transmitted to the Mars orbiter test system to check the consistency of the received landing rover simulation telemetry data and the data sent by the landing rover inter-device communication simulator.

[0096] Specifically, the inspection results can verify the correctness of the wireless demodulation threshold of the Mars orbiter inter-device communication device, and verify the electromagnetic self-compatibility of the signal reception of the inter-device communication device with other subsystems.

[0097] Specifically, the correctness of the wireless demodulation threshold of the Mars orbiter inter-device communication device can be verified, and the electromagnetic self-compatibility of the signal reception of the inter-device communication device and the operation of other subsystems can be verified.

[0098] Data processing steps: Organize the test data of the electromagnetic compatibility test of the Mars orbiter and analyze the test data.

[0099] Specifically, the test data of the electromagnetic compatibility test of the Mars orbiter in the above-mentioned first test step, the second test step and the third test step are collected and analyzed. For example, the measurement data exceeding the standard are analyzed, and the reasons for the exceeding of the standard are investigated, so as to realize the design and improvement of the electromagnetic compatibility of the Mars orbiter in the positive sample stage.

[0100] The present invention provides a Mars orbiter EMC test system, comprising:

[0101] Preparation module: Prepare the state for electromagnetic compatibility testing of the Mars orbiter.

[0102] Preferably, the preparation module comprises:

[0103] The first preparation submodule: place the Mars orbiter in a sealed state in a microwave darkroom.

[0104] The second preparation submodule: Place the Mars orbiter test system, lander rover simulation equipment and electromagnetic compatibility test system outside the microwave darkroom.

[0105] The third preparation submodule: The Mars orbiter in the microwave darkroom is interconnected with the Mars orbiter test system, the lander rover simulation equipment and the test equipment in the electromagnetic compatibility test system outside the microwave darkroom through wall test cables.

[0106] The first test module: environmental noise test in a microwave darkroom.

[0107] Preferably, the first test module includes:

[0108] The first test submodule: put the Mars orbiter in a power-off state; power on the Mars orbiter test system, the lander simulation equipment and the auxiliary equipment in the microwave darkroom; measure and record the environmental noise spectrum of the environmental noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system. If there is a strong interference signal in the measured environmental noise, check and locate the interference source of the strong interference signal, and isolate the wall-penetrating test cable or auxiliary equipment that leaks the strong interference signal or strengthen the coating with double-sided aluminum film.

[0109] The second test module: Conduct electromagnetic compatibility test between the Mars orbiter and the launch vehicle.

[0110] Preferably, the second test module includes:

[0111] The second test submodule: power on the Mars orbiter, set the working state according to the active segment, turn on the power supply to the lander and rover power supply equivalent device, and the lander and rover power supply and distribution simulator sets the power load value according to the active segment state of the lander and rover; place the radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, with the central axis of the radiation emission test antenna pointing to the lower plate of the Mars orbiter, and measure and record the radiation emission data of the Mars orbiter through electromagnetic radiation emission test equipment; place the radiation sensitivity test antenna near the Mars orbiter, adjust the distance between the radiation sensitivity test antenna and the side plate of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and output the test signal according to the transmission signal frequency band and power of the carrier rocket's transmitter through the electromagnetic radiation sensitivity test equipment to monitor whether the locking state and telemetry state of the Mars orbiter's transponder have abnormal jumps.

[0112] The third test module: Conduct electromagnetic compatibility testing on the simulated flight process of the Mars orbiter during the Earth-Mars transfer phase.

[0113] Preferably, the third test module includes:

[0114] The third test submodule: set the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase; measure and record the field strength of each pyrotechnic installation position of the Mars orbiter through the pyrotechnic field strength test equipment, and verify whether the field strength of each pyrotechnic installation position meets the limit requirement; perform electrostatic discharge test on the Mars orbiter through electrostatic discharge test equipment; test the demodulation threshold of the Mars orbiter's transponder through the radio frequency test subsystem; the Mars orbiter simulates the flight according to the typical stages of the flight process in the Earth-Mars transfer phase, and monitors the stability of the telemetry signals of each subsystem of the Mars orbiter and the correctness of the detection data of the payload subsystem during the simulated flight.

[0115] The fourth test module: Conduct electromagnetic compatibility testing on the simulated flight process of the Mars orbiter during the Mars circum-Mars phase.

[0116] Preferably, the fourth test module includes:

[0117] The fourth test submodule: the subsystems of the Mars orbiter are set to work in accordance with the maximum working mode of the Mars orbiting flight phase; the lander and rover inter-device communication simulator outputs the inter-device return signal, and adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, while observing the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the lander and rover inter-device communication simulator sends a set of landing rover simulated telemetry data, which are received by the Mars orbiter inter-device communication machine and then forwarded by the integrated electronic subsystem and the measurement and control subsystem to the Mars orbiter test system to check the consistency between the received landing rover simulated telemetry data and the data sent by the landing rover inter-device communication simulator.

[0118] Data processing module: organize the test data of the electromagnetic compatibility test of the Mars orbiter and analyze the test data.

[0119] The present invention can test the electromagnetic compatibility of the Mars orbiter during the initial prototype development stage, verify the electromagnetic compatibility between the Mars orbiter and the carrier rocket, and verify the self-compatibility of the subsystems inside the Mars orbiter and the electromagnetic compatibility of the communication interface with the lander and rover, providing a basis for the electromagnetic compatibility design and improvement of the Mars orbiter during the prototype stage, and helping to ensure that the electromagnetic compatibility requirements of the lander and rover are met after the Mars orbiter is docked with the lander and the carrier rocket.

[0120] Those skilled in the art know that, in addition to implementing the system, device and its various modules provided by the present invention in a purely computer-readable program code, it is entirely possible to implement the same program in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers and embedded microcontrollers by logically programming the method steps. Therefore, the system, device and its various modules provided by the present invention can be considered as a hardware component, and the modules implementing various programs included therein can also be considered as structures within the hardware component; the modules implementing various functions can also be considered as both software programs implementing the method and structures within the hardware component.

[0121] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A Mars orbiter EMC test method, characterized in that: include: Preparation step: preparing the state of the electromagnetic compatibility test of the Mars orbiter; The first test step: perform environmental noise test in a microwave darkroom; Second test step: performing electromagnetic compatibility test between the Mars orbiter and the carrier rocket; The third test step: performing an electromagnetic compatibility test of the Mars orbiter during a simulated flight process during the Earth-Mars transfer phase; Fourth test step: performing an electromagnetic compatibility test of the simulated flight process of the Mars orbiter during the Mars orbiting phase; Data processing step: collating the test data of the electromagnetic compatibility test of the Mars orbiter and analyzing the test data.

2. The Mars orbiter EMC testing method according to claim 1, characterized in that: The preparation steps include: Step S101: placing the Mars orbiter in a sealed state in the microwave darkroom; Step S102: placing the Mars orbiter test system, the lander simulation equipment and the electromagnetic compatibility test system outside the microwave darkroom; Step S103: The Mars orbiter in the microwave darkroom is interconnected with the Mars orbiter test system, the lander rover simulation equipment and the test equipment in the electromagnetic compatibility test system outside the microwave darkroom through a through-wall test cable.

3. The Mars orbiter EMC testing method according to claim 2, characterized in that: The first testing step comprises: Step S201: the Mars orbiter is in a power-off state; Step S202: Powering on the Mars orbiter test system, the lander simulation device, and the auxiliary equipment in the microwave darkroom; Step S203: Measure and record the environmental noise spectrum of the environmental noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system. If there is a strong interference signal in the measured environmental noise, check and locate the interference source of the strong interference signal, and isolate the through-the-wall test cable or the auxiliary equipment that leaks the strong interference signal or strengthen the coating with double-sided aluminum film.

4. The Mars orbiter EMC testing method according to claim 3, characterized in that: The second testing step comprises: Step S301: Power on the Mars orbiter, set the working state according to the active segment, turn on the power supply to the lander and rover power supply and distribution equivalent device, and set the power load value of the lander and rover power supply and distribution simulator according to the active segment state of the lander and rover; Step S302: placing a radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, with the central axis of the radiation emission test antenna pointing to the lower plate of the Mars orbiter, and measuring and recording the radiation emission data of the Mars orbiter by the electromagnetic radiation emission test equipment; Step S303: placing a radiation sensitivity test antenna near the Mars orbiter, adjusting the distance between the radiation sensitivity test antenna and the side panel of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and outputting a test signal through the electromagnetic radiation sensitivity test equipment according to the transmission signal frequency band and power of the transmitter of the carrier rocket to monitor whether the locking state and telemetry state of the transponder of the Mars orbiter have abnormal jumps.

5. The Mars orbiter EMC testing method according to claim 2, characterized in that: The third testing step comprises: Step S401: setting the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase; Step S402: measuring and recording the field strength of each pyrotechnic device to be installed position of the Mars orbiter by using an pyrotechnic device field strength testing device to verify whether the field strength of each pyrotechnic device to be installed position meets the limit requirement; Step S403: performing an electrostatic discharge test on the Mars orbiter by using an electrostatic discharge test device; Step S404: testing the demodulation threshold of the transponder of the Mars orbiter by means of the radio frequency test subsystem; Step S405: the Mars orbiter performs simulated flight according to typical stages of the flight process of the Earth-Mars transfer stage, and monitors the stability of telemetry signals of each subsystem of the Mars orbiter and the correctness of detection data of the payload subsystem during the simulated flight; The fourth testing step comprises: Step 501: each subsystem of the Mars orbiter is set to a working state according to the maximum working mode of the Mars orbiting flight phase; Step 502: the lander rover inter-device communication simulator outputs an inter-device return signal, adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, and simultaneously observes the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the lander rover inter-device communication simulator sends a set of lander rover simulation telemetry data, which is received by the Mars orbiter inter-device communication machine and then forwarded by the integrated electronic subsystem and the measurement and control subsystem to the Mars orbiter test system, to check the consistency between the received lander rover simulation telemetry data and the data sent by the lander rover inter-device communication simulator.

6. A Mars orbiter EMC test system, characterized in that: include: Preparation module: performing state preparation for electromagnetic compatibility test of the Mars orbiter; The first test module: environmental noise test in a microwave darkroom; The second test module is to perform an electromagnetic compatibility test between the Mars orbiter and the carrier rocket; The third test module: conducting an electromagnetic compatibility test of the simulated flight process of the Mars orbiter during the Earth-Mars transfer phase; The fourth test module: conducting an electromagnetic compatibility test of the simulated flight process of the Mars orbiter during the Mars orbiting phase; Data processing module: organizes the test data of the electromagnetic compatibility test of the Mars orbiter and analyzes the test data.

7. The Mars orbiter EMC test system according to claim 6, characterized in that: The preparation module comprises: The first preparation submodule is to place the Mars orbiter in the microwave darkroom in a sealed state; The second preparation submodule: placing the Mars orbiter test system, the lander simulation equipment and the electromagnetic compatibility test system outside the microwave darkroom; The third preparation submodule: the Mars orbiter in the microwave darkroom and the Mars orbiter test system outside the microwave darkroom, the lander rover simulation equipment and the test equipment in the electromagnetic compatibility test system are interconnected through a through-wall test cable.

8. The Mars orbiter EMC test system according to claim 7, characterized in that: The first test module comprises: The first test submodule: put the Mars orbiter in a power-off state; power on the Mars orbiter test system, the lander simulation equipment and the auxiliary equipment in the microwave darkroom; measure and record the environmental noise spectrum of the environmental noise in the microwave darkroom through the electromagnetic radiation emission test equipment in the electromagnetic compatibility test system, if there is a strong interference signal in the measured environmental noise, check and locate the interference source of the strong interference signal, isolate the through-the-wall test cable or the auxiliary equipment that leaks the strong interference signal, or strengthen the coating with double-sided aluminum film.

9. The Mars orbiter EMC test system according to claim 8, characterized in that: The second test module comprises: The second test submodule: power on the Mars orbiter, set the working state according to the active stage, turn on the power supply to the lander and rover power supply and distribution equivalent device, and the lander and rover power supply and distribution simulator sets the power load value according to the active stage state of the lander and rover; place the radiation emission test antenna at a preset position away from the docking surface of the Mars orbiter and the carrier rocket, the central axis of the radiation emission test antenna points to the lower plate of the Mars orbiter, and the radiation emission data of the Mars orbiter is measured and recorded by the electromagnetic radiation emission test equipment; place the radiation sensitivity test antenna near the Mars orbiter, adjust the distance between the radiation sensitivity test antenna and the side plate of the Mars orbiter and the installation height of the radiation sensitivity test antenna, so that the beam of the radiation sensitivity test antenna covers the Mars orbiter at the closest distance, and output the test signal according to the transmission signal frequency band and power of the transmitter of the carrier rocket by the electromagnetic radiation sensitivity test equipment to monitor whether the locking state and telemetry state of the transponder of the Mars orbiter have abnormal jumps.

10. The Mars orbiter EMC test system according to claim 7, characterized in that: The third test module comprises: The third test submodule: setting the working state of each subsystem of the Mars orbiter according to the maximum working mode during the orbital flight in the Earth-Mars transfer phase; measuring and recording the field strength of each pyrotechnic installation position of the Mars orbiter through the pyrotechnic field strength test equipment, and verifying whether the field strength of each pyrotechnic installation position meets the limit requirement; performing an electrostatic discharge test on the Mars orbiter through the electrostatic discharge test equipment; testing the demodulation threshold of the transponder of the Mars orbiter through the radio frequency test subsystem; the Mars orbiter simulates the flight according to the typical stages of the flight process in the Earth-Mars transfer phase, and monitoring the stability of the telemetry signals of each subsystem of the Mars orbiter and the correctness of the detection data of the payload subsystem during the simulated flight; The fourth test module comprises: The fourth test submodule: the subsystems of the Mars orbiter are set to work in accordance with the maximum working mode of the Mars orbiter flight phase; the lander and rover inter-device communication simulator outputs an inter-device return signal, adjusts the power of the inter-device return signal emitted by the inter-device communication antenna by changing the attenuation value of the inter-device link adjustment device, and observes the telemetry signal of the receiving signal level of the Mars orbiter inter-device communication machine at the same time, so that the receiving signal level of the Mars orbiter inter-device communication machine is equal to the demodulation threshold level; the lander and rover inter-device communication simulator sends a set of landing rover simulated telemetry data, which are received by the Mars orbiter inter-device communication machine and then forwarded by the integrated electronic subsystem and the measurement and control subsystem to the Mars orbiter test system to check the consistency of the received landing rover simulated telemetry data with the data sent by the landing rover inter-device communication simulator.

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